Abstract: An aircraft lamp includes: a lamp outer housing configured by a lamp housing having an opening and a cover attached to the lamp housing in a state where the opening is closed, wherein an internal space is formed as an arrangement space; a light source unit arranged in the arrangement space and having a light source; and a control unit including a control substrate that controls an ON/OFF of the light source, and a shielding plate that shields noise generated in the control substrate. The lamp housing is provided with a unit accommodation portion having a concave shape and an insertion/removal port. The control substrate is configured to be accommodated in and removed from the unit accommodation portion via the insertion/removal port. At least a part of the insertion/removal port is closed by the shielding plate in a state where the control substrate is accommodated in the unit accommodation portion.

Abstract: The present disclosure provides methods and systems for operating a rotorcraft comprising a plurality of engines configured to provide motive power to the rotorcraft. The rotorcraft is operated in a first flight regime. A target output power range for at least one of the plurality of engines is determined, the target output power range associated with operating the rotorcraft in a second flight regime different from the first flight regime in which at least one first engine of the plurality of engines is operated in an active mode to provide motive power to the rotorcraft and at least one second engine of the plurality of engines is operated in a standby mode to provide substantially no motive power to the rotorcraft. A graphical representation of the target output power range for the second flight regime is produced via a flight display in a cockpit of the rotorcraft.

Abstract: Methods and systems for providing location information for a user-selected feature on an active vertical situation display (VSD) in a cockpit of an aircraft. The method includes rendering the VSD having a plurality of terrain and weather features; receiving, from a user interface, the user-selected feature from among the plurality of features on the VSD, the plurality of features including terrain features and weather features; causing a reticle to be displayed as an overlay, centered, on the user-selected feature on the VSD, responsive to receiving the user-selected feature; rendering a horizontal extension from a center of the reticle to an intersection on a vertical axis of the VSD, and a vertical extension from the center of the reticle to an intersection on a horizontal axis of the VSD. An elevation label and a distance label are positioned on the respective extensions.

Abstract: An exterior helicopter light is configured to be mounted to a helicopter, in particular to an underside of the helicopter, the helicopter having a longitudinal axis (A). The exterior helicopter light comprises: a first set of light sources configured for emitting, in operation, light of a first color into a at least one rear sector of a ground below the helicopter, the at least one rear sector spatially extending around a projection of a rear portion of the helicopter onto the ground; and second set of light sources configured for emitting, in operation, light of a second color, which differs from the first color, into at least two forward sectors of the ground below the helicopter.

Abstract: A vertical landing vehicle including an airframe forming a hull and having at least one wing coupled to the airframe, at least one proximity sensor coupled to the airframe, and a flight control system including a control processor and an operator interface, wherein the at least one proximity sensor is coupled to the control processor, wherein the control processor, based on signals from the at least one proximity sensor, is configured to generate, for presentation through the operator interface, situational awareness indications corresponding to portions of the hull sensed by the at least one proximity sensor and obstacles sensed by the at least one proximity sensor, and wherein the situational awareness indications comprise a terrain map overlay including positional relationships between the hull and the obstacles.

Abstract: Embodiments of a method and system for sensing an obstacle, a computer device, and a computer-readable storage medium are provided. The method can include: capturing continuously, by first and second cameras adjacently arranged on a motor vehicle, obstacles around the motor vehicle, to obtain at least a first obstacle image and a second obstacle image respectively; associating the first obstacle image with the second obstacle image; determining whether the first obstacle image and the second obstacle image comprise the same obstacle. By means of some of the disclosed methods and systems, an obstacle can be real-time sensed by a motor vehicle in a large field of view, such as, a range of 360° around the vehicle.

Abstract: Disclosed is a configuration to control automatic return of an aerial vehicle. The configuration stores a return location in a storage device of the aerial vehicle. The return location may correspond to a location where the aerial vehicle is to return. One or more sensors of the aerial vehicle are monitored during flight for detection of a predefined condition. When a predetermined condition is met a return path program may be loaded for execution to provide a return flight path for the aerial vehicle to automatically navigate to the return location.

Abstract: Described herein are systems and methods of determining a pose of a camera within a vehicle scene. In one embodiment, a method includes the initial step of capturing an image of the vehicle scene from the camera. At step, reference data indicative of the vehicle scene is loaded, the reference data includes positions and orientations of known features within the vehicle scene. Next, at step, the geometric appearance of one or more of the known features is identified within the image. Finally, at step, the three dimensional position and orientation of the camera relative to the known features identified in step c) is determined from the geometric appearance, and a pose of the camera within the vehicle scene is calculated.

Abstract: An aerodynamic blade is provided and includes a blade body and a light module. The blade body includes an inboard end and a tip outboard of the inboard end. The blade body is connectable with a hub at the inboard end such that rotations of the hub drive rotations of the tip about a rotational axis. The light module is disposed in the tip and configured to activate in response to the rotations of the tip about the rotational axis to emit light visible at an exterior of the blade body.

Abstract: A guidance camera deployed on a vehicle may be equipped with a zoom lens configured to change a zoom level of the guidance camera. The zoom level may be changed in response to a scenario performed by a vehicle equipped with the guidance camera, vehicle controls issued by a vehicle controller, and/or based on identification of objects in imagery captured by the guidance camera. The zoom lens may be implemented as a lens array that includes different lenses, as a wheel lens array that includes different lenses, or by a light direction device that guides light from a specific lens of different lenses into the guidance camera. Stereo cameras may be configured with the zoom lenses, and may be repositioned to ensure suitable overlap in a field of view to enable calculation of a distance of objects captured in the imagery of the stereo camera.

Abstract: Systems and methods for displaying range and time to altitude for an aircraft are disclosed. In embodiments, a system includes a flight management system configured to receive flight data from a plurality of sensors, wherein the flight data includes altitude and vertical speed measurements. The system further includes an aircraft display system and controller. The controller is in communication with the flight management system and the aircraft display system. The controller is configured to receive a selected target altitude and generate a range to altitude arc at a display of the aircraft display system based on the flight data and the selected target altitude. The controller is further configured to determine a time to altitude based on the flight data and the selected target altitude and configured to present the time to altitude in proximity to the range to altitude arc at the display of the aircraft display system.

Abstract: An aircraft pilot assistance system is disclosed. In one aspect, the system includes at least one primary chain and at least one secondary chain. Each chain can include a plurality of interconnected electronic modules, the primary and secondary chains differing from one another by at least one electronic module. Each chain can be configured at least to retrieve pilot assistance information and to implement at least one of the following avionics functions: automatic piloting, flight plan management and trajectory development, and alert generation in case of malfunction of the aircraft or in case of detection of at least one risk on the trajectory. The primary chain can be configured to operate according to a nominal pilot assistance information retrieval mode, and the secondary chain can be configured to operate according to a downgraded mode in which the information from the nominal mode is partially retrieved.

Abstract: Embodiments are directed to flight instrument warnings that are configured to automatically adjust a low airspeed warning band on an airspeed indicator based on available torque margin and radar altimeter height. Warnings may be presented on a primary flight display or on flight instruments when a low airspeed band is entered.

Abstract: A photographing device includes a first image sensor, a first filter area, a second image sensor, a first distance calculating unit, and a second distance calculating unit. The first image sensor includes a first sensor receiving light of a first wavelength band and outputting a target image, and a second sensor receiving light of a second wavelength band and outputting a reference image. The first filter area transmits a first light of a third wavelength band, which includes at least part of the first wavelength band, the first light being a part of light incident on the first image sensor. The second image sensor outputs a first image. The first distance calculating unit calculates a first distance to an object captured in the target image and the reference image. The second distance calculating unit calculates a second distance to an object captured in the reference image and the first image.

Abstract: A vertical landing vehicle including an airframe forming a hull and having at least one wing coupled to the airframe, at least one proximity sensor coupled to the airframe, and a flight control system including a control processor and an operator interface, the at least one proximity sensor being coupled to the control processor, the control processor being configured to receive proximity signals from the at least one proximity sensor and present, through the operator interface and based on the proximity signals, situational awareness information of obstacles within a predetermined distance of the vertical landing vehicle relative to the hull and/or the at least one wing.

Abstract: An engine assembly comprising an engine and a pod surrounding the engine that is equipped, upstream according to the direction of entry of air into the engine, with a fan provided with blades, the pod having an upstream air intake. The engine assembly also comprises a display unit including at least one light ring arranged in the air intake upstream of the fan, the light ring including at least one row of light-emitting diodes and being configured to emit at least one light beam and to project it on the blades of the fan.

Abstract: A method for modeling a cell site with an Unmanned Aerial Vehicle (UAV) includes causing the UAV to fly a given flight path about a cell tower at the cell site, wherein a launch location and launch orientation is defined for the UAV to take off and land at the cell site such that each flight at the cell site has the same launch location and launch orientation; obtaining a plurality of photographs of the cell site during about the flight plane, wherein each of the plurality of photographs is associated with one or more location identifiers; and, subsequent to the obtaining, processing the plurality of photographs to define a three dimensional (3D) model of the cell site based on the associated with one or more location identifiers and one or more objects of interest in the plurality of photographs.

Abstract: Disclosed is a configuration to control automatic return of an aerial vehicle. The configuration stores a return location in a storage device of the aerial vehicle. The return location may correspond to a location where the aerial vehicle is to return. One or more sensors of the aerial vehicle are monitored during flight for detection of a predefined condition. When a predetermined condition is met a return path program may be loaded for execution to provide a return flight path for the aerial vehicle to automatically navigate to the return location.

Abstract: A control method and system for controlling a main rotor of a rotorcraft to perform a stage of flight in auto-rotation. The control system has a control member for controlling the collective pitch of the blades of the main rotor. The control member is movable over an amplitude of positions between two extreme physical stops. A calculation unit calculates a collective pitch angle for the blades of the main rotor, referred to as an “auto-rotation collective pitch”. This enables the main rotor to rotate at a speed of rotation that is optimum for the stage of flight in auto-rotation of the rotorcraft. A motor means controls the position of the control member at a predetermined position, referred to as the “auto-rotation position”, in which the control member generates a control setpoint for servo-controlling the current collective pitch of the blades of the main rotor on the “auto-rotation collective pitch”.

Abstract: A control system for a rotorcraft, which system includes at least one control unit allowing a rotor of a rotorcraft to be driven, with the rotorcraft including at least three independent landing-gear units, with each landing-gear unit including means for detecting a ground reaction force F1, F2, F3 exerted on the landing-gear unit when the rotorcraft is in contact with the ground, and with the control system being suitable for receiving information from the detection means. The invention also relates to the rotorcraft and to a control method corresponding to the control system.

Abstract: An unmanned aerial vehicle (UAV) may be used for delivering products or other articles. The UAV is configured to detect the presence of nearby people, animals, or other interactive objects. Upon detecting a nearby object, the UAV may produce speech in order to warn or instruct the object. The UAV may also have speech input capabilities in order to capture and respond to speech from the object. The UAV may conduct a speech dialog with a nearby person in order to request information and/or answer questions from the object. In certain situations, the UAV may detect whether an object is in the way of a desired landing area and may communicate with the object through speech to ask the object to move or to ask the object to specify an alternative landing area.

Abstract: Systems and methods for protecting an airborne platform against collisions are provided. One system includes FMCW radar sensors including transmitting antennae, means for receiving signals from echoes and for processing and digitizing same, and means for sending a central unit data representing said digital signals via a dedicated point to point link. The central unit includes means for processing said data to detect obstacles, means for calculating parameters for each obstacle including its radial velocity, distance range and azimuth, and means to transmit an avionic system of said platform data representing said detected obstacles and parameters. The system further includes means for guaranteeing that said emitted signals are shifted in time to create a shift in frequency guaranteeing that the radar sensors operate in the whole frequency band without perturbing each other.

Abstract: A safety system includes an apparatus-mounted projector capable of projecting a warning image onto a designated danger zone about a dangerous implement of the apparatus. The projector is in signal communication with an electronic control module configured to control the warning image depending on a measured or received operational state of the apparatus implement. The projected warning image can include static, dynamic, or static and dynamic image elements depending on the measured or received operational state of the implement.

Abstract: A method of assisting in the navigation of a rotorcraft by displaying in flight a dynamic representation of the outside world (Me) in the event of a loss of visibility (brown-out/white-out). Front maps with incorporated localization are generated on the basis of front images captured by a set of front cameras. Terrain elevation data is generated from images captured by complementary sets of lateral and rear cameras. In the event of a loss of visibility, a reconstituted world (Mr) is prepared from the front maps with incorporated localization. On request of the pilot, an extrapolated world (Mex) is prepared by adding terrain elevation data to the front maps with incorporated localization, in compliance with the common time and the relative positions of the various sets of cameras between one another.

Abstract: A method for operating a device to protect an application from unauthorized operation is provided. The application will fail to operate on the device when the device is defined outside a selected operating region. The method includes transmitting the selected operating region for the application, and receiving the application and a geographic identifier associated with the application. The geographic identifier is configured to identify the selected operating region wherein the application will operate on the device. The method further includes transmitting a request to execute the application on the device. The request includes the geographic identifier. Further included in the method is receiving a code. The code prevents an execution of the application on the device if the code is a disable code. The disable code indicates that the device is operating outside the selected operating region. An apparatus for content protection in a wireless network is also provided.

Abstract: A method and system for maintaining visual vertical reference on a rotorcraft display during rotorcraft landing is provided. The method generates vertical poles and positions them on the rotorcraft display such that vertical reference as well as roll information may be quickly and easily comprehended by a pilot.

Abstract: An apparatus and method are provided for displaying a predicted image for rotocraft flight in consideration of data associated with a selected flight procedure and a current image.

Abstract: Methods and systems are provided for alerting a driver of a vehicle having a transparent conformal display unit. In one embodiment, a method includes: detecting that an object is located in proximity to the vehicle based on sensor data; determining at least one of a time and a distance associated with the detected object based on vehicle conditions; generating an image that illustrates the at least one of time and distance based on vehicle conditions; and selectively generating a display signal to display the image on a transparent display of the vehicle through the transparent conformal display unit.

Abstract: A collision avoidance and warning system for a helicopter uses a type of emitted energy, for example radio frequency radar, from a transceiver positioned to cover a selected field of view for detecting an object or pedestrian in the vicinity of the helicopter. For helicopters that include a tail rotor assembly, the selected field of view can include a region around the tail rotor assembly so that when the helicopter is running on the ground, an alarm can be issued to persons approaching the tail rotor assembly. When the helicopter is in flight, the collision avoidance and warning system can alert the pilot when a portion of the helicopter outside of the pilot's field of view is in danger of a collision with an object.

Abstract: A vehicle comprises an acceleration sensing module and a crash direction-computing module. The acceleration-sensing module is configured for generating acceleration information resulting from a vehicle collision event. The acceleration information includes a first direction acceleration value and a second direction acceleration value. The crash direction-computing module is coupled to the acceleration-sensing module for receiving the acceleration information therefrom and is configured for determining impact direction information resulting from the vehicle collision event.

Abstract: Embodiments of the invention describe apparatuses, systems, and methods related to data capture of objects and/or an environment. In one embodiment, a user can capture time-indexed three-dimensional (3D) depth data using one or more portable data capture devices that can capture time indexed color images of a scene with depth information and location and orientation data. In addition, the data capture devices may be configured to captured a spherical view of the environment around the data capture device.

Abstract: A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available.

Abstract: This is an electrical system not an electronic one. The light units should be placed as close to an actual circle as possible. For a helicopter visual landing in rough seas, low visibility and darkness, the approach for landing becomes a hazardous task. Good visibility of the landing area will be possible due to this system effectiveness. The helicopter can now become a truly all-weather vehicle. No new technology is needed. The parts for the system can be purchased off a store shelf, a minor modification of an existing item, or made by relatively minor fabrication.

Abstract: Methods and systems involving an incentivized recovery of balloon materials are disclosed herein. An example system may be configured to: (a) determine a landing location of a balloon, where the balloon has been configured to operate as a node in a balloon network; (b) detect a removal event corresponding to the balloon ceasing to operate as a node in the balloon network and descending to the landing location; and (c) in response to detecting the removal event, initiate a transmission of a recovery-assistance signal that is comprised of (i) location data corresponding to the landing location of the balloon and (ii) an indication of an incentive to recover the balloon.

Abstract: Methods and systems for use in locating and prioritizing cargo are provided. The system includes a communications unit configured to receive location information and content information for each of a plurality of pieces of cargo from a cargo location and classification sensor (CLCS). The system also includes a cargo pickup planner module configured to determine a priority listing of pieces of cargo based on mission information, the location information, and the content information. The system also includes a cargo approach planner module configured to transmit a set of waypoints for specified pieces of cargo selected from the priority listing to a control system (FCS) configured to maneuver a vehicle to a position above a specified piece of cargo. The system further includes a cargo pickup overlay generator module configured to generate an overlay for a pilotage system (PS) display to assist a user in maneuvering the vehicle above each piece of cargo for pickup.

Abstract: This is an electrical system not an electronic one. The light units should be placed as close to an actual circle as possible. For a helicopter visual landing in rough seas, low visibility and darkness, the approach for landing becomes a hazardous task. Good visibility of the landing area will be possible due to this system effectiveness. The helicopter can now become a truly all-weather vehicle. No new technology is needed. The parts for the system can be purchased off a store shelf, a minor modification of an existing item, or made by relatively minor fabrication.

Abstract: A method of designating and communicating a desired LZ to an aircraft includes outputting a coded laser signal at or near a desired landing zone to indicate a location of the desired landing zone. The coded laser signal is received by an aircraft that desires to land at the desired landing zone. The location of the desired landing zone and an ingress path from a current location of the aircraft to the desired landing zone are determined by a processor provided with the aircraft.

Abstract: An example flight display for an aircraft includes a virtual ice accretion meter display having a liquid water content portion and an ice thickness portion. The ice thickness portion is configured to display a virtual ice thickness value.

Abstract: Provided is a low atmosphere ascent and descent observation experimental tool. Since a position of a radiosonde and a ground captive position of the radiosonde is accurately grasped using a GPS radiosonde, accurate observation results may be obtained.

Abstract: A rotorcraft (1) having on-board lighting equipment for lighting the surrounding environment. The lighting equipment comprises a plurality of headlights (2, 2?, 3, 3?) that are allocated to respective specific lighting functions in landing and in winching. The headlights (2, 2?, 3, 3?) are also operated to perform a searching lighting function. Control means determine which headlights (2, 2?, 3, 3?) are to be operated depending on a lighting function selected by an operator and depending on where the headlights are located on the rotorcraft (1). A search zone (4, 4?) for illuminating is identified by identification means on the basis of a lighting command common to the headlights (2, 2?, 3, 3?). Coordination means cause the headlights (2, 2?, 3, 3?) to converge on the identified search zone (4, 4?), while taking account of their respective locations on the rotorcraft (1).

Abstract: A method of assisting the piloting of an aircraft (1) comprising a first rotor (5) having a plurality of first blades (6) with a first variable collective pitch, and a second rotor (7) having a plurality of second blades (8) with a second variable collective pitch. According to the method, a computer determines a power limit curve (70) and displays said limit curve (70) in a diagram (60) to inform the pilot of the first and second collective pitch margins available before reaching the limits of at least one operating rating of the power plant of the aircraft.

Abstract: An apparatus for displaying terrain on a display apparatus of an airborne vehicle is provided. The apparatus includes a synthetic vision system having a terrain and obstruction database, an enhanced vision system with sensors for recording terrain data, a height and position sensor for determining the flight state data, a display apparatus, a processor for fusion of the data from the synthetic vision system and from the enhanced vision system. The height information that is produced by the synthetic vision system and the enhanced vision system is stored as pixels in a two-dimensional grid network. The fusion processor uses an error function for insertion of a pixel into the two-dimensional grid network. The error function provides an estimate of the size of the respective cell in which the pixel is stored, from the distance between the pixel and the sensor position.

Abstract: The present application relates to a system and method for providing real-time indications of economic impact of aircraft operations to an aircraft operator. The system and method allow the aircraft operator to reduce economic impact during flight of the aircraft. Such an analysis and cue to the aircraft operator allows the operator to make real-time changes during flight to reduce damage of life-limited aircraft components, thereby reducing the economic impact of aircraft operation that is directly associated with maintenance and component replacement. The system and method can also include pre-flight and post-flight analysis methods for reduction of economic impact of flight operations.

Abstract: A system and method, that will allow helicopter pilots to air taxi from an instrument approach to an airport to a designated landing area or pad, includes symbology characterizing an approach aim point different from an aim point for aircraft landing on the runway, and symbology indicating an air taxi route from the approach aim point to a landing pad.

Abstract: A method of presenting attitude and heading information of a vehicle on a display to a viewer inside the given vehicle, comprising the steps of: using a 2D display, using data provided by an inertial reference system, using a computer and graphical software for treating the data and defining graphical elements, depicting the graphical elements in 3D on the 2D display, and presenting the attitude and heading information on the 2D display by associating them to at least one graphical element.

Abstract: A method for presenting the current drift values of an aircraft on a display device in which the drift values are presented in a vector presentation. The length of the drift vector above a predefined threshold value is presented in a manner proportional to the current drift velocity, and the length of the drift vector below the threshold value is presented in a manner disproportionate to the current drift velocity. There is a continuous transition between the two ways of presentation at the threshold value.

Abstract: Methods and systems involving an incentivized recovery of balloon materials are disclosed herein. An example system may be configured to: (a) determine a landing location of a balloon, where the balloon has been configured to operate as a node in a balloon network; (b) detect a removal event corresponding to the balloon ceasing to operate as a node in the balloon network and descending to the landing location; and (c) in response to detecting the removal event, initiate a transmission of a recovery-assistance signal that is comprised of (i) location data corresponding to the landing location of the balloon and (ii) an indication of an incentive to recover the balloon.

Abstract: A system may include a sensor for coupling with a vehicle configured for atmospheric flight. The sensor may be configured for detecting a turbulence event, where the turbulence event is at least one of experienced by the vehicle or occurs proximal to the vehicle during atmospheric flight. The system may also include a transmitter coupled with the sensor. The transmitter may be configured for automatically remotely transmitting data regarding the turbulence event to a ground based entity.

Abstract: A loading system for loading a cargo hold (2) of an aircraft (1), containers, pallets or like ULDs (20) for accommodating freight being introduced into the cargo hold through an access opening, being transported by means of a transport device (60) and being fastened in transport positions. With the ULDs are identification devices (30), e.g. RFID transponders, which identification devices have storage devices for storing first data, especially identification data. The system comprises at least one first reading device (40) for reading the first data of a ULD introduced into the cargo hold, and at least one first transmitter device (50) for transmitting the first data to at least one first recipient (11).

Abstract: A system and method, that will allow helicopter pilots to air taxi from an instrument approach to an airport to a designated landing area or pad, includes symbology characterizing an approach aim point different from an aim point for aircraft landing on the runway, and symbology indicating an air taxi route from the approach aim point to a landing pad.